FIELD: engines and pumps.
SUBSTANCE: gas turbine engine comprises a rotary adjustable inlet guide vane located prior to the low pressure compressor. Angle of inclination of the inlet guide vane is set when the engine is started in such a way as to increase the air flow entering the compressor. This is particularly useful when the gas turbine engine is restarted when the aircraft equipped with it is in the air. Method for starting a gas turbine engine and a nozzle with a variable cross-sectional square are also disclosed.
EFFECT: invention is intended to increase the speed of rotation of the compressor and the turbine rotors in the autorotation mode.
20 cl, 3 dwg
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